Dhivya, S. and Karthikeyan, A. (2018) Design and Analysis of Gas Turbine Blade with Cooling. EAI Endorsed Transactions on Energy Web and Information Technologies.
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Abstract
The turbine inlet temperature in advanced gas turbine engine is very high and it is above the melting point of blade material. In this project radial convective cooling method is used. The turbine blade with cooling holes (6, 8, 9,10, and 11) is designed using CATIA V5. The models are analyzed using
| Item Type: | Article |
|---|---|
| Date Deposited: | 04 Mar 2026 11:33 |
| Last Modified: | 12 Apr 2026 06:43 |
| URI: | http://eprints.eai.eu/id/eprint/19539 |
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